CN104350238A - 覆盖有耐磨涂层的涡轮机定子壁 - Google Patents
覆盖有耐磨涂层的涡轮机定子壁 Download PDFInfo
- Publication number
- CN104350238A CN104350238A CN201380029247.XA CN201380029247A CN104350238A CN 104350238 A CN104350238 A CN 104350238A CN 201380029247 A CN201380029247 A CN 201380029247A CN 104350238 A CN104350238 A CN 104350238A
- Authority
- CN
- China
- Prior art keywords
- support structure
- motor stator
- turbine motor
- annular turbine
- described support
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/005—Selecting particular materials
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/40—Casings; Connections of working fluid
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/522—Casings; Connections of working fluid for axial pumps especially adapted for elastic fluid pumps
- F04D29/526—Details of the casing section radially opposing blade tips
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/12—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part
- F01D11/122—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material
- F01D11/125—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using a rubstrip, e.g. erodible. deformable or resiliently-biased part with erodable or abradable material with a reinforcing structure
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/10—Stators
- F05D2240/11—Shroud seal segments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/40—Organic materials
- F05D2300/44—Resins
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/603—Composites; e.g. fibre-reinforced
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/614—Fibres or filaments
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2300/00—Materials; Properties thereof
- F05D2300/70—Treatment or modification of materials
- F05D2300/702—Reinforcement
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Laminated Bodies (AREA)
Abstract
涡轮机定子的环形部分,其包括结构支撑(10),该结构支撑提供有接连的锁控亚层(12)和由填充有微珠的树脂形成的耐磨涂层(14),锁控亚层确保耐磨涂层粘结由长纤维的纤维股所形成的结构支撑,当耐磨涂层固定于结构支撑时,其周缘部分(12A、12B)固定到结构支撑和其中心部分(12C)嵌入在微珠填充的树脂中。
Description
背景技术
本发明涉及提供有耐磨涂层的涡轮发动机定子壁,并且特别地用在航空发动机中,诸如风扇保持壳体或低压压气机壳体。
这种壳体可以由多个接触壁扇体组成,该多个接触壁扇体一起围绕由燃烧气体驱动旋转的旋转叶片。壁也可以包括封闭结构或由两个半外壳组成。为了确保几乎没有间隙地进行运转,和由此为了确保涡轮发动机在消耗和效率方面提供所要求的性能,旋转叶片需要接触壳体上所设置的耐磨涂层。通常,耐磨涂层由基于树脂的材料构成,该树脂填充有包含由耐火材料所制造的中孔微珠类型的产生孔的试剂,并且通常地,通过模塑或者例如,通过热喷涂在待要被保护的表面上的物理沉积形成涂层。
不幸地,根据结构部分的性质,即,根据它们是由金属制造还是由复合材料制造,可以发现耐磨材料可以失去粘性,导致它变得分离和由此或多或少量构成涂层的材料被涡轮发动机的旁路流所吸入。
为了解决该粘性损失问题,已知在沉积热保护之前,砂磨或研磨结构部分。不幸地,该方案不能被推广到为了保护或钝化目的,已经接受电解或电化学处理的表面,因为这种操作具有破坏特定处理的后果。
发明的目的和概述
本发明的主要目的由此是通过提出无论是金属还是复合材料制造的,具有可以覆盖任何类型表面的耐磨涂层的定子壁来减轻这种缺陷,该定子壁不会受到这种局部的粘性分离。
通过包括结构支撑的环形涡轮发动机定子部分达到该目的,该结构支撑提供有接连的粘合底层和由填充有微珠的树脂形成的耐磨涂层,定子部分的特征在于:通过由长纤维制造的纤维加强形成用于将所述耐磨涂层固定到所述结构支撑的所述粘合底层,所述耐磨涂层固定在所述结构支撑时,该纤维加强具有固定到所述结构支撑的加强的周缘部分以及具有用所述填充有微珠的树脂浸渍的其中心部分。
因此,因为耐磨涂层通过长纤维制造的纤维加强,所以耐磨涂层牢固地固定于结构支撑,因此避免任何局部分离。本发明由此特别地适于其中不可能通过研磨或砂磨进行任何表面制备的,由阳极化铝制造的定子壳体部分。
在有利的准备中,所述纤维加强包括二维(2D)长纤维织物的一个或多个并列股。所述纤维加强可以包括玻璃纤维的非浸渍2D织物股或任何其它长纤维加强,或者实际上用玻璃纤维的2D织物或任何其它长纤维加强在它们的周缘至少部分地预浸渍的多个股。
根据另一个有利的准备,所述结构支撑可以基于金属合金,并且所述周缘部分通过环氧树脂粘性地粘合到所述结构支撑,或者实际上它可以基于复合材料,并且所述周缘部分与制备所述结构支撑时的所述结构支撑共固化。
优选地,填充有微珠的所述树脂是聚硅氧烷树脂或环氧树脂,并且所述微珠是中空的玻璃或耐火材料的微珠。
有利地,所述耐磨涂层通过热喷涂、注射、模塑或实际上涂布的沉积固定于所述结构支撑,以这样的方式以浸渍所述纤维加强和所述结构支撑。
本发明也提供了任何涡轮发动机定子,其包括如上所述的环形部分。
附图说明
从表示具有非限制特征的实施方式的参考附图进行的下面描述,呈现本发明的其它特征和优点,并且其中:
图1是由金属制造的本发明环形涡轮发动机定子部分的截面图;和
图2是由复合材料制造的环形涡轮发动机定子部分的截面图。
具体实施方式
图1是例如,通过在圆周方向上首尾相连将多个扇体连接在一起形成的轴向涡轮发动机风扇的一部分保持壳体的截面图。壳体围绕由多个叶片组成的旋转组件(未示出),同时壳体内表面和叶片顶端之间的间隙是零或几乎是零。
该环形定子部分包括在内侧上(面对燃烧气体的流)提供的结构支撑10和接连的粘合层12;以及由带孔的耐磨材料制造的热保护涂层14,并且叶片顶端可以部分地穿入到该孔中,而不会受到严重磨损。
在该第一实施方式中,结构支撑10由金属合金制造,例如钛或铝合金制造。
热保护涂层14由带孔的材料制造,并且在运转中通常所遇到的温度下具有令人满意的强度。常规地,为了构造该耐磨涂层,必须依靠基于聚硅氧烷或环氧树脂的材料,该材料填充有耐火材料,并且特别地玻璃制造的中空微珠类型的产生孔的试剂。
在本发明中,用于粘合耐磨涂层和结构支撑表面的粘合底层12由在其周缘部分地固定于结构支撑10的玻璃纤维的加强或任何其它长纤维加强形成。
通过二维长纤维织物的一个或多个并置股构造纤维加强。当纤维加强仅有一个股时,优选地不浸渍(干燥)它,并且使用环氧树脂(或者当耐磨涂层是基于聚硅氧烷时,实际上聚硅氧烷树脂),它有利地在其周缘(或者至少沿着其侧边缘12A和12B中两个)粘性地粘合结构支撑10。相反,当复合加强包括多个股时,它们彼此独立,并且然后可以至少部分地在它们的周缘,特别地沿着它们的侧边缘先预浸渍它们,然后,例如,使用环氧树脂,通过沿着这些侧边缘粘性地粘合它们到结构支撑10而保持它们。例如,使用滚筒或喷枪有利地可以手动地进行该浸渍(手动层压)。
在这两种构造中,加强的中心部分12C是左侧自由的(即,不粘性地粘合到结构支撑),并且例如,通过热喷涂粉末,然而当织物是由金属长纤维制造时,使用已知的等离子沉积技术,在耐磨涂层的物理沉积期间浸渍它。在其它情况下,可以仅仅注射、模塑或涂布耐磨材料,通过这种方式以浸渍纤维加强和结构支撑的表面。
图2表示本发明的另一个实施方式,其更特别地适于由复合材料所制造的结构支撑10,通过环氧树脂中或具有相似性质的树脂中嵌入的由碳、玻璃、芳族聚酰胺或陶瓷纤维制造的纤维加强,以常规方式构造该复合材料。在这种情况下,在环氧树脂的帮助下,粘合底层12不在其周缘直接地粘合到结构支撑10上,但是优选地当制备结构支撑时一起与结构支撑共固化,以这样的方式以致于加强直接地与构成结构支撑表面的结构支撑本身的纤维加强10A结合。自然地,考虑确保该固化不影响保持自由的中心部分。然而,粘合底层12的结构与上述结构相同,并且由玻璃纤维的加强或包含二维长纤维织物的干燥股或多个预浸渍股的任何其它长加强纤维形成,然而,该任何其它长加强纤维与结构支撑一起固化和热粘性地粘合到结构支撑。
Claims (10)
1.环形涡轮发动机定子部分,其包括结构支撑(10),该结构支撑提供有接连的粘合底层(12)和由填充有微珠的树脂形成的耐磨涂层(14),定子部分的特征在于:通过由长纤维制造的纤维加强形成用于将所述耐磨涂层固定到所述结构支撑的所述粘合底层,该纤维加强只有加强的周缘部分(12A、12B)通过粘性粘合或通过共固化固定于所述结构支撑。
2.根据权利要求1的环形涡轮发动机定子部分,其特征在于:所述纤维加强包括二维长纤维织物的一个或多个并置股。
3.根据权利要求2的环形涡轮发动机定子部分,其特征在于:所述纤维加强包括玻璃纤维或任何其它长纤维加强的非浸渍的2D织物股。
4.根据权利要求2的环形涡轮发动机定子部分,其特征在于:所述纤维加强包括用玻璃纤维的2D织物或任何其它长纤维加强在它们的周缘至少部分地预浸渍的多个股。
5.根据权利要求1的环形涡轮发动机定子部分,其特征在于:当所述结构支撑是基于金属合金时,所述周缘部分通过环氧树脂粘性地粘合所述结构支撑。
6.根据权利要求1的环形涡轮发动机定子部分,其特征在于:当所述结构支撑是基于复合材料时,所述周缘部分与制备所述结构支撑时的所述结构支撑共固化。
7.根据权利要求1的环形涡轮发动机定子部分,其特征在于:所述填充有微珠的树脂是聚硅氧烷树脂或环氧树脂。
8.根据权利要求7的环形涡轮发动机定子部分,其特征在于:所述微珠是中空的玻璃或耐火材料的微珠。
9.根据权利要求1至8中任一权利要求的环形涡轮发动机定子部分,其特征在于:通过热喷涂、注射、模塑或实际上涂布的沉积,所述耐磨涂层固定于所述结构支撑,通过这种方式以浸渍所述纤维加强和所述结构支撑。
10.一种涡轮发动机定子,其包括根据权利要求1至9中任一权利要求的环形部分。
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1255169A FR2991374B1 (fr) | 2012-06-04 | 2012-06-04 | Paroi stator de turbomachine recouverte d'un revetement abradable |
FR1255169 | 2012-06-04 | ||
PCT/FR2013/051212 WO2013182782A1 (fr) | 2012-06-04 | 2013-05-30 | Paroi stator de turbomachine recouverte d'un revetement abradable. |
Publications (2)
Publication Number | Publication Date |
---|---|
CN104350238A true CN104350238A (zh) | 2015-02-11 |
CN104350238B CN104350238B (zh) | 2016-12-07 |
Family
ID=48656235
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201380029247.XA Active CN104350238B (zh) | 2012-06-04 | 2013-05-30 | 环形涡轮发动机定子部分以及包括该部分的定子 |
Country Status (8)
Country | Link |
---|---|
US (1) | US9803497B2 (zh) |
EP (1) | EP2861833B1 (zh) |
CN (1) | CN104350238B (zh) |
BR (1) | BR112014030181B1 (zh) |
CA (1) | CA2875371C (zh) |
FR (1) | FR2991374B1 (zh) |
RU (1) | RU2637302C2 (zh) |
WO (1) | WO2013182782A1 (zh) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2014120117A1 (en) * | 2013-01-29 | 2014-08-07 | United Technologies Corporation | Blade rub material |
CA3015841A1 (en) * | 2016-02-26 | 2017-08-31 | Standard Aero Limited | Coating for lining a compressor case |
US10472980B2 (en) * | 2017-02-14 | 2019-11-12 | General Electric Company | Gas turbine seals |
US10526908B2 (en) * | 2017-04-25 | 2020-01-07 | United Technologies Corporation | Abradable layer with glass microballoons |
KR102049051B1 (ko) * | 2018-08-22 | 2019-11-26 | 엘지전자 주식회사 | 팬 모터 및 그 제조방법 |
US12084977B1 (en) | 2023-10-10 | 2024-09-10 | Rolls-Royce North American Technologies Inc. | Gas turbine engine with fan track liner having triply periodic minimal surface reinforcement |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5388959A (en) * | 1993-08-23 | 1995-02-14 | General Electric Company | Seal including a non-metallic abradable material |
CN1417452A (zh) * | 2001-11-09 | 2003-05-14 | 三菱重工业株式会社 | 涡轮机及其制造方法 |
US20090214824A1 (en) * | 2004-06-29 | 2009-08-27 | Mtu Aero Engines Gmbh | Apparatus and method for coating a compressor housing |
EP2317079A2 (en) * | 2009-10-30 | 2011-05-04 | Alstom Technology Ltd | Abradable coating system |
Family Cites Families (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2628693A (en) * | 1947-05-16 | 1953-02-17 | Chrysler Corp | Nonsquealing bonded brake shoe |
US4289447A (en) * | 1979-10-12 | 1981-09-15 | General Electric Company | Metal-ceramic turbine shroud and method of making the same |
US4460185A (en) * | 1982-08-23 | 1984-07-17 | General Electric Company | Seal including a non-metallic abradable material |
US4436848A (en) * | 1983-04-12 | 1984-03-13 | Owens-Corning Fiberglas Corporation | Aqueous co-emulsions of epoxy resin and mineral oil |
US4639388A (en) * | 1985-02-12 | 1987-01-27 | Chromalloy American Corporation | Ceramic-metal composites |
US5951892A (en) * | 1996-12-10 | 1999-09-14 | Chromalloy Gas Turbine Corporation | Method of making an abradable seal by laser cutting |
GB2459844B (en) * | 2008-05-06 | 2011-01-19 | Rolls Royce Plc | Fan section |
-
2012
- 2012-06-04 FR FR1255169A patent/FR2991374B1/fr active Active
-
2013
- 2013-05-30 US US14/405,545 patent/US9803497B2/en active Active
- 2013-05-30 BR BR112014030181-6A patent/BR112014030181B1/pt active IP Right Grant
- 2013-05-30 EP EP13730010.9A patent/EP2861833B1/fr active Active
- 2013-05-30 CA CA2875371A patent/CA2875371C/fr active Active
- 2013-05-30 RU RU2014153637A patent/RU2637302C2/ru active
- 2013-05-30 CN CN201380029247.XA patent/CN104350238B/zh active Active
- 2013-05-30 WO PCT/FR2013/051212 patent/WO2013182782A1/fr active Application Filing
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5388959A (en) * | 1993-08-23 | 1995-02-14 | General Electric Company | Seal including a non-metallic abradable material |
CN1417452A (zh) * | 2001-11-09 | 2003-05-14 | 三菱重工业株式会社 | 涡轮机及其制造方法 |
US20090214824A1 (en) * | 2004-06-29 | 2009-08-27 | Mtu Aero Engines Gmbh | Apparatus and method for coating a compressor housing |
EP2317079A2 (en) * | 2009-10-30 | 2011-05-04 | Alstom Technology Ltd | Abradable coating system |
Also Published As
Publication number | Publication date |
---|---|
US20150139787A1 (en) | 2015-05-21 |
CA2875371A1 (fr) | 2013-12-12 |
US9803497B2 (en) | 2017-10-31 |
RU2637302C2 (ru) | 2017-12-01 |
BR112014030181B1 (pt) | 2021-10-19 |
RU2014153637A (ru) | 2016-07-27 |
CA2875371C (fr) | 2019-09-03 |
FR2991374A1 (fr) | 2013-12-06 |
CN104350238B (zh) | 2016-12-07 |
BR112014030181A2 (pt) | 2017-06-27 |
WO2013182782A1 (fr) | 2013-12-12 |
EP2861833B1 (fr) | 2016-09-28 |
EP2861833A1 (fr) | 2015-04-22 |
FR2991374B1 (fr) | 2016-04-08 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN104350238A (zh) | 覆盖有耐磨涂层的涡轮机定子壁 | |
CA2867913C (en) | Process for producing ceramic composite components | |
EP2257468B1 (en) | Single-piece propeller and method of making | |
US10046482B2 (en) | Method for manufacturing a turbomachine blade made of composite material | |
CN102116175B (zh) | 用于冲击区域增强的系统 | |
US9587506B2 (en) | Segment of an abradable ring seal for a turbomachine, and process for the manufacture of such a piece | |
CN109477458B (zh) | 风轮机叶片的前缘保护 | |
CN102705293B (zh) | 致动缸的缸体及其制造方法和混凝土泵送设备 | |
US8556579B2 (en) | Composite aerofoil blade with wear-resistant tip | |
CA2762639C (en) | Composite-material vane | |
JP6278191B2 (ja) | 複合材翼及び複合材翼の製造方法 | |
CN104271888A (zh) | 用于由复合材料制成的涡轮发动机叶片的金属结构增强件 | |
CN102806666A (zh) | 聚合物复合材料及其工艺 | |
US20230003133A1 (en) | Blade made of composite material with variable-density attached leading edge | |
EP2959113B1 (en) | Edge seal for gas turbine engine ceramic matrix composite component | |
US20180304442A1 (en) | Grinding body having reduced weight | |
CN102689436A (zh) | 致动缸的缸体的制造方法 | |
CN106584885A (zh) | 一种非金属材料制品的3d打印与玻璃钢复合制作工艺 | |
US20240239062A1 (en) | Vane made of composite material comprising a metallic reinforcement and method for manufacturing such a vane | |
US20240280027A1 (en) | Turbine engine airfoil with a woven core and woven layer | |
US12037938B1 (en) | Composite airfoil assembly for a turbine engine | |
CN114759702A (zh) | 一种新型转子结构的高速永磁电机 |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
C06 | Publication | ||
PB01 | Publication | ||
C10 | Entry into substantive examination | ||
SE01 | Entry into force of request for substantive examination | ||
C14 | Grant of patent or utility model | ||
GR01 | Patent grant |